| 摘要 |
A combustor (30) for a gas turbine engine includes a radially inboard liner (36), a radially outboard liner (38), and a bulkhead (34) that cooperatively define an annular combustion chamber (32), a plurality of first fuel injectors (54) that are disposed in the bulkhead (34), and a plurality of second fuel injectors (62) that are disposed in at least one of the inboard liner (36) and the outboard liner (38) aftward of the bulkhead (34). A method is also provided for operating the combustor (30) wherein fuel distribution between a forward combustion zone (60) and a downstream combustion zone (64) is selectively varied in response to the power operating mode of the gas turbine engine with an objective to control NOx formation. |
